DE102015009353A1 - Method of protecting a vehicle from attack by a laser beam - Google Patents

Method of protecting a vehicle from attack by a laser beam

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Publication number
DE102015009353A1
DE102015009353A1 DE102015009353.3A DE102015009353A DE102015009353A1 DE 102015009353 A1 DE102015009353 A1 DE 102015009353A1 DE 102015009353 A DE102015009353 A DE 102015009353A DE 102015009353 A1 DE102015009353 A1 DE 102015009353A1
Authority
DE
Germany
Prior art keywords
laser beam
vehicle
8th
missile
laser
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
DE102015009353.3A
Other languages
German (de)
Inventor
Arne Nolte
Michael Masur
Michael Gross
Nicolai Künzner
Thomas Kuhn
Norbert Stelte
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Diehl Defence GmbH and Co KG
Original Assignee
Diehl BGT Defence GmbH and Co KG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Diehl BGT Defence GmbH and Co KG filed Critical Diehl BGT Defence GmbH and Co KG
Priority to DE102015009353.3A priority Critical patent/DE102015009353A1/en
Publication of DE102015009353A1 publication Critical patent/DE102015009353A1/en
Application status is Withdrawn legal-status Critical

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41HARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
    • F41H11/00Defence installations; Defence devices
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41GWEAPON SIGHTS; AIMING
    • F41G7/00Direction control systems for self-propelled missiles
    • F41G7/20Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22Homing guidance systems
    • F41G7/2253Passive homing systems, i.e. comprising a receiver and do not requiring an active illumination of the target
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41GWEAPON SIGHTS; AIMING
    • F41G7/00Direction control systems for self-propelled missiles
    • F41G7/20Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22Homing guidance systems
    • F41G7/2273Homing guidance systems characterised by the type of waves
    • F41G7/2293Homing guidance systems characterised by the type of waves using electromagnetic waves other than radio waves
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41GWEAPON SIGHTS; AIMING
    • F41G7/00Direction control systems for self-propelled missiles
    • F41G7/20Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/30Command link guidance systems
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41HARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
    • F41H13/00Means of attack or defence not otherwise provided for
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42BEXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/01Arrangements thereon for guidance or control

Abstract

The invention relates to a method for protecting a vehicle (2) from attack by a laser beam (8). The vehicle (2) can be quickly and effectively protected against a high energy laser beam (8) when a sensor system (16) of the vehicle (2) detects laser radiation of the laser beam (8) and a control unit (20) of the vehicle (2) detects the laser beam (8) from the data of the sensor system (16) recognizes as such, a start of a missile (12, 14) for the protection of the vehicle (2) in front of the laser beam (8) by the control unit (20) is controlled and the missile (12 14) starts from the vehicle (2).

Description

  • The invention relates to a method for protecting a vehicle from attack by a laser beam.
  • High-energy lasers can transmit very high power over several kilometers and over a longer period of time. With such services, sensitive parts of vehicles can be so severely damaged or destroyed within a few seconds that the functioning of the vehicles is jeopardized. Thus, for example, aircraft can be attacked from the ground, in particular slow-moving commercial aircraft with relatively low maneuverability are particularly vulnerable.
  • It is therefore an object of the present invention to provide an effective method for protecting a vehicle from attack by a laser beam.
  • This object is achieved by a method of the type mentioned above, wherein the invention detects a sensor system of the vehicle laser radiation of the laser beam and a control unit of the vehicle detects the laser beam from the data of the sensor system as such, a start of a missile to protect the vehicle from the laser beam is controlled by the control unit and the missile starts from the vehicle. The missile can shade the vehicle and / or approach and combat a laser source emitting the laser beam. This is done expediently so quickly that the laser energy deposited on the vehicle has not yet led to threatening damage. A fast protection can be achieved by starting the missile from the vehicle, since then the missile is already on site and dive into the laser beam for shading and / or can quickly fly to combat the laser source on this.
  • Especially in the latter case, the missile is expediently equipped with a rocket motor.
  • The method is particularly suitable for use against a high energy laser source or a high energy laser beam. Also advantageous is a defense of a sturgeon laser. The sensor system comprises at least one sensor sensitive to laser radiation, which detects the laser radiation of the laser beam. For this purpose, the sensor or the sensor system is expediently sensitive in a radiation spectrum which is usually used for high-energy lasers or interfering lasers. To facilitate the detection of stray radiation, the spectrum in which the sensor is sensitive may be limited to a band around the one laser wavelength commonly used for high energy lasers. For example, the band is at most ± 100 nm around the wavelength of 3800 nm. In addition, the sensor expediently recognizes characteristics typical of laser radiation, such as the presence of coherent radiation. Further, it is advantageous if the sensor system detects by means of image processing methods, a laser beam as such in the environment, for example on the basis of scattered radiation. For this purpose, the sensor system advantageously contains an image sensor, for example a matrix detector.
  • The sensor system detects laser radiation of the laser beam, ie radiation directly emitted by the laser source and / or laser radiation scattered from the laser beam, for example by the scattering of the laser beam in the air, on particles and / or on an object. The sensor system absorbs the radiation and converts it into a measuring signal. From the measurement signal, the control unit expediently determines a threat level of the laser radiation, for example by a classification in at least the levels threatening or harmless. This can be done, for example, via the measured scattered light intensity in the atmosphere, an energy input into the sensor system, a spread spectrum and / or over a temporal characteristic of the radiation, such as a pulsation.
  • The vehicle is preferably an aircraft, and may be fixed-wing aircraft or a rotorcraft, such as a helicopter. However, the invention is also advantageously applicable for protecting a land vehicle or a watercraft. The vehicle may be a manned or unmanned vehicle.
  • The control unit may have one or more arithmetic units that can be arranged in the vehicle at a location distributed over the vehicle, in the vehicle and in the missile or exclusively in the missile housed in the vehicle - and thus likewise in the vehicle. The control unit recognizes the laser beam as such and initiates a start of the flying body as a function of the recognition result. If a laser beam is recognized as such and it is also classified as threatening to the vehicle, the missile is launched from the vehicle. If a laser beam is not recognized as such or classified as non-threatening, the launching of the missile expediently fails.
  • The missile is expediently a guided missile and in particular an unmanned missile. He can use a rocket engine and / or an air-breathing engine, such as For example, a turbine drive, be equipped. In this case, an air-breathing engine is advantageous in accompanying the vehicle by the missile, and a rocket motor is more advantageous in an intended fight the laser source. Also possible is a missile without its own engine, for example in the form of a steering column. The missile expediently comprises a control unit which steers the missile, for example parallel to the vehicle and / or to the laser source.
  • In an advantageous embodiment of the invention, the sensor system picks up the laser beam from the side, and the control unit detects the laser beam from sensor data obtained from the recording from the side, in particular exclusively from these sensor data. In this way, the laser beam can already be detected, even if he has not yet hit the vehicle, so that early detection of the laser beam as such is possible. In addition, since in a recording of the side only in the air scattered radiation of the laser beam is recorded, can be dispensed with a strong combustion protection of the sensor system. As a result, an image acquisition is facilitated because unprotected, image-processing sensors can be used. A laser beam recorded from the side can be recognized as a straight line in the environment and can thus be recognized as such by means of image processing methods.
  • Due to the high energy input of the laser beam when hitting the sensor system, this can be destroyed within milliseconds. In order nevertheless to obtain the detection capability of the sensor system, it is advantageous if the sensor system has a plurality of laser-sensitive sensors. These are expediently arranged at different positions on the outer shell of the vehicle so that they can detect the laser beam from different locations. If one of the sensors is hit and destroyed by the laser beam, the sensory activity of the sensor system can be continued or resumed by another sensor. The sensors are expediently spaced apart at a distance of more than one meter. In particular, in each case at least one sensor is arranged in at least two regions of the group: front half of the fuselage, rear half of the fuselage, upper half of the fuselage, lower half of the fuselage, on a wing. By a wide distance of the sensors from each other can also be achieved the further advantage that a position calculation of a laser source by triangulation from the sensor data of at least three sensors is possible. In this way, the position of the laser source can be determined easily, and the missile can be instructed to this position.
  • In order to counteract targeted and rapid destruction of the sensors by a movement of the laser beam directed at the sensors, it is advantageous if at least one sensor of the sensor system is covered during operation of the sensor system. In particular, regular operation provides that one sensor is always covered by several sensors of the sensor system. In a surprising attack, at least this part of the sensors can be preserved and used for the detection of the laser beam. It is advantageous in that only a part of the sensors of the sensor system is directed into the environment of the vehicle and another part of the sensors is covered against the environment. Furthermore, it is advantageous if at least one covered sensor is directed into the environment depending on the functionality of one of the other sensors, in particular is brought from a passive state into an active state. If one sensor fails, another can be brought from the covered state to the active state directed to the environment, and the detection of the laser beam can be continued. For example, while the vehicle is in motion, a first sensor can permanently examine the surroundings of the vehicle for laser radiation. If this sensor fails, for example because it was hit by the laser beam, another sensor is activated at another position of the vehicle for further observation and thereby directed or opened into the environment.
  • Another advantageous possibility for maintaining the functionality of the sensor system is that the sensor system has a multiple sensor with multiple sensor heads. These can, for example, be directed one after the other into the environment. Advantageously, at least one of the sensor heads is always concealed, while at least one other of the sensor heads is directed into the environment and detected. The multiple sensor may be, for example, a turret sensor carrying a plurality of sensors on a drum. Also possible are successively used sensors, the front sensor or an element connected to it, covering the underlying sensor.
  • Particularly in the case of an aircraft, it is advantageous if at least one sensor of the sensor system is directed exclusively into an upper half space above the vehicle. In an attack of a laser beam from below, the sensor, especially if it is permanently directed in the above half-space, not be hit directly. A detection of the laser beam is still possible on the detection of scattered radiation.
  • The launched by the vehicle missile can be used to combat the laser source, which emits the laser beam. For this purpose, the missile can fly directly into the laser source and / or destroy the laser source by a detonation charge, in particular by a cone-shaped forward splitter charge. For this purpose, it is advantageous to know the position of the laser source, either relative to the position and / or direction of movement of the vehicle or in absolute coordinates. If the laser beam is sensed by a sensor from the side, it can be determined as a straight line with an abrupt end. The end point of the line can be equated with the position of the laser source.
  • In this respect, it is advantageous if the control unit determines from the data of the sensor system the position of a laser source which emits the laser beam. In this case, a radiation end of the laser beam can be detected and the position of the laser source can be determined from the position of the beam. Alternatively or additionally, the position from triangulation can be determined from the data of several sensors. The position of the laser source can be detected as a direction, for example as an absolute direction or as a direction relative to the direction of flight of the aircraft. It is also possible to determine the direction as an absolute, ie geographical, direction.
  • Furthermore, a determination of a distance of the laser source from the sensor system is advantageous. This can be done particularly easily using a flying height of the vehicle. If the direction of the laser source and the altitude are known, the distance to the laser source can be calculated from this in a simple manner, in particular taking into account topographical data of an overflown landscape.
  • In order to enable rapid control of the laser source, it is advantageous if the launch of the missile is fully automatic and in particular triggered by the detection of the laser beam. Alternatively, a semi-automatic triggering is possible in which an operator of the vehicle gives an enable signal and triggering takes place only after the release signal, in particular fully automatically, for example, only when a direction or position of the laser source has been detected with sufficient certainty and accuracy. A start of the missile is expediently already before an alignment of the laser beam on the vehicle, so before the vehicle was hit by the laser beam.
  • The launch of the missile can take place from a starting device, for example from a container. This can be mounted in the fuselage of the vehicle, so that in particular several missiles can be started in a salvo shot simultaneously or immediately sequentially to protect the vehicle. The term "start" may in this case include a launch.
  • In order to enable a very fast control of the laser source, it is advantageous if an alignment of a starting device of the missile takes place as a function of the position of the laser beam, in particular in dependence on the position of the laser source. It can be a targeted launch in the direction of the laser source, so that the time is saved for a detour flight. Accordingly, it is advantageous if the missile starts directed to a laser source of the laser beam. In this case, a curved trajectory, for example, taking into account ballistic influences, are used so that the alignment of the missile at the start does not have to be in a straight line to the laser source.
  • Further, it is advantageous if the control unit in the missile passes a target instruction on a laser source of the laser beam to a control unit of the missile. This can be done before the launch of the missile and / or in particular during the flight of the missile, for example by a data link from the vehicle to the missile. The control unit of the missile receives the target instruction and directs the missile to the laser source. In this way, the missile can already be started before the exact position of the laser source has been calculated.
  • The flight of the missile can be controlled independently by a control unit of the missile. Additionally or alternatively, it is possible that the remaining in the vehicle control unit controls the flight of the missile or mitsteuert. For example, the self-controlling missile an escape or Abschattungsanweisung be issued by the vehicle, which is then taken into account by the control unit of the missile.
  • A control of the missile from the vehicle is also advantageous if the position of the laser beam or the laser source can be accurately determined by the vehicle or the vehicle detects an impact of the laser beam and delegates the missile in a shading position. Thus, for example, laser-sensitive areas of the vehicle can be deliberately shadowed by the corresponding flight control of the missile, or the onward flight of the missile can be controlled in the case of a destroyed sensor of the missile further to the laser source.
  • The invention is also directed to a vehicle having a sensor system for detecting a laser beam. According to the invention, the vehicle is equipped with a missile which is prepared for controlling a laser source of the laser beam and / or for shading an element of the aircraft. Advantageously, the aircraft includes a control unit which is prepared to detect the laser beam from the data of the sensor system as such and to control a start of the missile from the vehicle to protect the vehicle from the laser beam.
  • The description of advantageous embodiments of the invention given so far contains numerous features that are summarized in several dependent claims in several groups. However, these features may conveniently be considered individually and grouped together into meaningful further combinations, in particular when reclaiming claims, so that a single feature of a dependent claim can be combined with a single, several or all features of another dependent claim. In addition, these features can be combined individually and in any suitable combination both with the method according to the invention and with the device according to the invention according to the independent claims.
  • Thus, process features can also be formulated formally as properties of the corresponding device unit and functional device features also as corresponding process features.
  • The above-described characteristics, features, and advantages of this invention, as well as the manner in which they are achieved, will become clearer and more clearly understood in connection with the following description of the embodiments, which will be described in detail in conjunction with the drawings. The embodiments serve to illustrate the invention and do not limit the invention to the combination of features specified therein, not even with respect to functional features. In addition, suitable features of each embodiment may also be explicitly considered isolated, removed from one embodiment, incorporated into another embodiment to complement it, and / or combined with any of the claims.
  • Show it:
  • 1 an aircraft immediately before an attack by a laser system,
  • 2 a turret sensor of a sensor system of the aircraft and
  • 3 several defenses of the aircraft with the help of missiles.
  • 1 shows a vehicle 2 in the form of an aircraft, which in this case is designed as an airliner for the transport of passengers or airfreight. In a landscape 4 about which the vehicle 2 flies, is a laser system 6 positioned in the in 1 represented moment a laser beam 8th by a laser source 10 is generated, aimed at the sky. The laser system 6 is placed in the embodiment shown on the ground and immovable. However, it is also possible that the laser system 6 is movable and mounted for example in an aircraft. All described below and the laser source 10 Related details are then adjusted accordingly to the mobility or height above the ground.
  • The laser system 6 is a high energy laser system that uses the laser beam 8th emits primarily in the infrared spectral range, for example, at 3.8 microns, wherein the laser beam 8th transported enough energy over a distance of several kilometers to destroy sensitive parts of the aircraft and thereby endangering its flying capacity. The laser system 6 is used to combat aircraft and has a control unit that controls the laser beam 8th on the vehicle 2 pivots and the laser beam 8th automates the movement of the aircraft 2 readjusts. In the control unit is a laser-sensitive point of the vehicle 2 deposited on which the laser beam 8th By means of image processing methods is automatically directed to those in the laser system 6 pictorially deposited location of the aircraft 2 over a period of a few seconds to irradiate and thereby destroy.
  • Instead of the high energy laser system 6 For example, a designator laser system or marking laser system can be fought or disturbed that the vehicle 2 Illuminates to a guided missile in the vehicle 2 to control. By a shading of the vehicle 2 and / or destruction of the laser source 10 This mark can be disturbed, so that the attacking missile the vehicle 2 can not find. The following description relates to a stationary high energy laser system 6 without being limited to this system.
  • To protect the vehicle 2 this has at least one missile 12 . 14 on, in 1 to explain several protection methods three missiles 12 and a missile 14 are shown. Furthermore, the aircraft has a sensor system 16 with a plurality of sensors 18 on, each with a control unit 20 signal technically connected. In the exemplary embodiment shown, the aircraft is with five sensors 18 one in the rear half of the fuselage, one in the front half of the fuselage, one on each wing of the aircraft and one sensor upwards 18 on the upper half of the fuselage of the aircraft.
  • To protect the aircraft is initially only one of the sensors 18 of the sensor system 16 active, and the other of the sensors 18 are covered. Covered in this context means that the laser-sensitive element of the corresponding sensor 18 is covered by a laser-resistant cover such that it by an external to the aircraft 2 radiating laser beam 8th not destroyed, in particular can not be achieved. Active means in this context that a field of view of the laser-sensitive element is free in the environment and the sensor 18 Record sensor data and to the control unit 20 passes. This safety measure can be achieved that not all sensors 18 by several laser beams 8th or by a laser beam traveling very fast over the fuselage 8th be destroyed before the laser beam 8th was recognized. Due to the wide distance of the sensors 18 apart from each other will also be a quick scanning of the individual sensors 18 through the laser beam 8th difficult. In addition, one of the sensors 18 oriented upwards and through the bottom of the aircraft 2 radiating laser beam 8th not available. Aligned upward means, in particular in this context, that the sensor 18 is aimed at a horizontal flight of the aircraft exclusively in the upper half-space. This sensor 18 is thus very well protected and also suitable for the laser beam 8th from scattered radiation of the laser beam 8th to recognize in the atmosphere.
  • At the in 1 shown embodiment is the front sensor 18 of the sensor system 16 active and the other sensors 18 are covered. The sensor is designed as a revolver sensor and schematically in 2 shown.
  • 2 shows one of the sensors 18 of the sensor system 16 out 1 , The sensor 18 includes six sensor heads 22 of which five are the sensor heads 22 through a cover 24 , For example, a metal plate covered. One of the sensor heads 22 lies behind an opening 26 of the cover 24 , is thus oriented in the environment and can look into the environment and detect laser radiation. The sensor heads 22 are pivotable about a common axis, as in 2 indicated by the curved arrow. Is the currently active sensor head 22 destroyed, the revolver can be further rotated by 60 °, so that the next sensor head 22 behind the opening 26 comes to rest and record the detection.
  • In the middle and also behind the cover element 24 arranged is another sensor head 28 which has the task of detecting if a high energy laser beam 8th on the sensor 18 is directed. The sensor head 28 Although not able to detect laser radiation itself, but it measures an energy input on the cover 24 , so that an active switching an undamaged sensor head 22 can be avoided as long as the laser beam 8th on the sensor 18 is directed.
  • The rest of the sensors 18 of the aircraft 2 can like the in 2 illustrated sensor 18 be executed. In a simplified version, however, the remainder of the sensors point 18 only one sensor head 22 and the sensor head 28 and a movable cover member 24 on. As long as the laser beam 8th directed to the sensor, the cover conceals the laser radiation-sensitive sensor head 22 , Only when the control unit 20 has enabled the activation of the sensor and as an additional condition the laser beam 8th not on the sensor 18 resting, the sensor head becomes 22 and thus the sensor 18 switched active.
  • The sensor heads 22 each comprise image sensors behind a 180 ° optics, so that the scenery of a hemisphere of the surrounding space is imaged onto a laser-sensitive element. This allows an image of the laser beam 8th can be recorded in the environment, and from this can provide more information about the laser beam 8th be determined, such as geometry, position and intensity of the laser beam. From the geometry recognizes the control unit 20 of the sensor system 16 in particular by means of image processing methods, the laser beam 8th as such. As geometrical features can be used that the laser beam is seen as a straight line in the landscape. It also has a sharply defined end at the laser source 10 on. At its other end, however, the laser beam becomes weaker, as long as it does not strike an object 1 is shown, so that a defined end is not readily determinable. This feature of the upper attenuation of the laser radiation can also be used for laser detection.
  • From the geometrical data of the laser beam 8th as well as its spectrum and radiation intensity classifies the control unit 20 the laser beam 8th first in the three stages harmless, potentially dangerous and dangerous. In a classification in the level harmless the laser beam 8th which is generated by a laser pointer, for example, is further observed, but neither the laser beam becomes 8th the laser source is still shading 10 fought. at a classification into one of the other two levels is a shadowing and / or combat prepared. This is a canister 30 , the at least one of the missiles 12 houses, in the direction of the laser source 10 pivoted. This pivoting is in 1 through the curved double arrow on the canister 30 indicated. Alternatively or additionally, the ejection of the missile 14 from the fuselage of the aircraft 2 prepared. Classification into the highest of the threat classes will initiate combat and / or shadowing. This is for example a release of an operator of the aircraft 2 , for example, a pilot, necessary. However, this has already been given in advance, for example because it is known that the aircraft is flying through a potentially dangerous region.
  • Both for shading and to combat the laser source 10 It is advantageous if the position of the laser source 10 is known. This determines the control unit 20 for example, from the geometry of the laser beam 8th , So, in place of the abrupt end of the laser beam 8th the laser source 10 be suspected. In addition, the laser beam can 8th be given a direction, at least a rough direction at the top and bottom, the laser source 10 only at a lower end of the laser beam 8th is positioned. In this way, a direction of the laser source 10 relative to the aircraft 2 be determined. From the direction and altitude of the aircraft, and conveniently a topography of the overflown landscape, the distance between the aircraft and the laser source can also be determined 10 In particular, the absolute geographic coordinates of the laser source are determined 10 certainly.
  • The detection of the laser beam 8th takes place insofar by a recording of the laser beam 8th from the side, being out of the laser beam 8th At the atmosphere scattered laser radiation is recorded. This can also be done by the sensor pointing upwards 18 done, whose view of the laser source 10 is displaced. Based on the orientation of the visible part of the laser beam 8th can also be a further course of the laser beam 8th be extrapolated in the area.
  • In the event that the laser beam 8th already on the aircraft 2 is directed and thus the undefined upper end is no longer recognizable as such and the laser beam 8th Both up and down has an abrupt end, the determination of the position of the laser source 10 through another of the sensors 18 of the sensor system 16 be made, for example by a sensor 18 on a wing of the aircraft 2 , This detects the laser beam 8th in itself and both abrupt ends, the control unit 20 the lower abrupt end of the laser beam 8th as the location of the laser source 10 selects. Also possible is a position determination of the laser source 10 by triangulation. Once three or more sensors 18 the laser beam 8th can be detected and its lower abrupt end determined, in addition to the direction of the laser source 10 also their removal by the known orientation of the sensors 18 on the aircraft 2 be determined to each other.
  • To protect the aircraft is now at least one missile 12 . 14 started from the aircraft. The control of the start takes over the control unit 20 of the sensor system 16 which also forms part of a central vehicle control of the vehicle 2 can be.
  • 3 shows two embodiments for protecting the aircraft, which can be performed individually or in combination. In a first embodiment, a missile 12 started in the form of a steering rocket. This missile 12 gets out of the canister 30 started, for example, by a drop, a launch and / or a launch of a missile engine of the missile 12 , Because the missile 12 by the orientation of the canister 30 on the laser source 10 already to the laser source 10 oriented, detours can be avoided and the missile 12 in direct line to the laser source 10 sent. As an alternative to the guided missile, other guided missiles may also be used, for example steerable projectiles. This is also a control unit 32 for controlling the steered flight and a steering system 34 to carry out the steering. Next includes the missile 12 expediently an active part 36 with an explosive charge to combat the laser source 10 , Depending on the design of the missile 12 have a rocket motor for independent acceleration.
  • The control of the missile 12 can independently by the control unit 32 of the missile 12 respectively. It is also possible that the control by the control unit 20 the aircraft takes place, either in addition or independently by the specification of appropriate commands to the control unit 32 of the missile 12 , That way, the missile becomes 12 on or in the laser source 10 controlled so that it is destroyed. Just before the missile 12 the laser source 10 reached, the active part can 36 be ignited, which hurls a splinter charge cone forward and the laser source 10 destroyed by this. The ignition of the active part 36 can be done by an impact fuse or a proximity fuse located in the missile head.
  • The flight of the missile 12 is suitably by the laser beam 8th guided. For this purpose, this can be done by the sensor system 16 of the aircraft and in the missile 12 appropriate control signals can be given. Alternatively or additionally, it is possible that the missile 12 the laser beam 8th independently used as a flight guidance and depending on its orientation in space directs its own flight. The missile 12 thus flies guided by the laser beam 8th independently in the laser source 10 , This can be the flight in the laser beam 8th or outside along the laser beam 8th or with a suitably predetermined distance at the laser beam 8th be guided along.
  • In particular, in an independent control of the missile 12 to the laser source 10 is the transfer of a destination instruction from the control unit 20 to the control unit 32 advantageous. As a result, at least a rough navigation in the first part of the approach can be considerably facilitated.
  • In the other embodiment, the missile 14 dropped from the fuselage of the aircraft, and this begins its flight, which is substantially parallel to the flight of the aircraft. The purpose of this flight is the aircraft, in particular at least laser-sensitive locations of the aircraft 2 , from the laser beam 8th shade off. The missile 14 is powered by an air-breathing internal combustion engine, such as a turbine, so that a long flight is possible in the company of the aircraft. Alternatively or additionally, a rocket motor is possible, in particular a solid fuel motor, which is tuned in terms of its performance on the airspeed of the aircraft. The missile 14 is equipped with large wings for large-scale shading of the aircraft. At least the entire lower side of the missile 14 is laser-hardened, so that it can be irradiated for at least two minutes by the high-energy laser beam 8th no destruction affecting the flight on the missile 14 generated.
  • To hold the missile 14 in the laser beam 8th There are several possibilities. For example, the position of the laser beam 8th in the room or its end on the vehicle 2 through sensors 18 of the sensor system 16 be determined. Appropriate control signals are from the control unit 20 to a control unit 40 of the missile 14 given.
  • An alternative or additional possibility is that the missile 14 determines the shading itself and from this regulates his flight. This is how the missile points 14 an upward-facing laser-sensitive sensor on the aircraft 2 observed from below. An impact of the laser beam 8th on the aircraft 2 is detected, and the missile 14 is controlled so that the irradiation spot of the laser beam 8th on the aircraft 2 disappears. For this purpose, the flight is controlled so that the control variable, namely the visibility of the laser spot on the aircraft 2 , disappears or at least decreases. This is achieved by a particular complete shading. On the other hand, if the laser beam 8th away from the aircraft, the laser spot also disappears. In this case, the missile accompanies 14 the aircraft still a predetermined distance or duration of time to provide protection against the potentially dangerous laser beam 8th to maintain.
  • LIST OF REFERENCE NUMBERS
  • 2
    vehicle
    4
    landscape
    6
    laser system
    8th
    laser beam
    10
    laser source
    12
    missile
    14
    missile
    16
    sensor system
    18
    sensor
    20
    control unit
    22
    sensor head
    24
    cover
    26
    opening
    28
    sensor head
    30
    canister
    32
    control unit
    34
    steering system
    36
    active part
    38
    rocket engine
    40
    control unit

Claims (15)

  1. Method for protecting a vehicle ( 2 ) from attack by a laser beam ( 8th ), in which a sensor system ( 16 ) of the vehicle ( 2 ) Laser radiation of the laser beam ( 8th ) and a control unit ( 20 ) of the vehicle ( 2 ) the laser beam ( 8th ) from the data of the sensor system ( 16 ) as such, a launch of a guided missile ( 12 . 14 ) to protect the vehicle ( 2 ) in front of the laser beam ( 8th ) from the control unit ( 20 ) and the guided missile ( 12 . 14 ) from the vehicle ( 2 ) starts.
  2. Method according to claim 1, characterized in that the sensor system ( 16 ) the laser beam ( 8th ) from the side and the control unit ( 20 ) the laser beam ( 8th ) from sensor data obtained from the page shot.
  3. Method according to claim 1 or 2, characterized in that the sensor system ( 16 ) several laser-sensitive sensors ( 18 ) provided by different positions of the outer shell of the vehicle ( 2 ) the laser beam ( 8th ).
  4. Method according to claim 3, characterized in that only a part of the sensors ( 18 ) in the environment of the vehicle ( 2 ), another part of the sensors ( 18 ) is covered against the environment and at least one covered sensor ( 18 ) depending on the functionality of one of the other sensors ( 18 ) is directed into the environment.
  5. Method according to one of the preceding claims, characterized in that the sensor system ( 16 ) a multiple sensor with multiple sensor heads ( 22 ), which can be successively directed into the environment.
  6. Method according to one of the preceding claims, characterized in that at least one sensor ( 18 ) of the sensor system ( 16 ) exclusively in an upper half-space above the vehicle ( 2 ).
  7. Method according to one of the preceding claims, characterized in that the control unit ( 20 ) from the data of the sensor system ( 16 ) a radiating end of the laser beam ( 8th ) and from the position of the beam end, the position of a laser source ( 10 ) determining the laser beam ( 8th ).
  8. A method according to claim 7, characterized in that a distance to the laser source ( 10 ) using an altitude of the vehicle ( 2 ) is determined.
  9. Method according to one of the preceding claims, characterized in that the start of the guided missile ( 12 . 14 ) is fully automatic and by detecting the laser beam ( 8th ) is triggered.
  10. Method according to one of the preceding claims, characterized in that an alignment of a starting device ( 30 ) of the guided missile ( 12 ) depending on the position of the laser beam ( 8th ) he follows.
  11. Method according to claim 10, characterized in that the guided missile ( 12 ) directed to a laser source ( 10 ) of the laser beam ( 8th ) starts.
  12. Method according to one of the preceding claims, characterized in that the control unit ( 20 ) the guided missile ( 12 . 14 ) a targeting to a laser source ( 10 ) of the laser beam ( 8th ) passes.
  13. Method according to one of the preceding claims, characterized in that the control unit ( 20 ) from the aircraft ( 2 ) from a flight of the missile ( 12 . 14 ) controls.
  14. Method according to claim 13, characterized in that the control unit ( 20 ) a position of the laser beam ( 8th ) in the room and the flight of the missile ( 12 . 14 ) using the determined position.
  15. Vehicle ( 2 ) with a sensor system ( 16 ) for detecting a laser beam ( 8th ), a guided missile ( 12 . 14 ) and a control unit ( 20 ), which is prepared to use the laser beam ( 8th ) from the data of the sensor system ( 16 ) as such and a start of the missile ( 12 . 14 ) from the vehicle ( 2 ) to protect the vehicle ( 2 ) in front of the laser beam ( 8th ) to control.
DE102015009353.3A 2015-07-17 2015-07-17 Method of protecting a vehicle from attack by a laser beam Withdrawn DE102015009353A1 (en)

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DE102015009353.3A DE102015009353A1 (en) 2015-07-17 2015-07-17 Method of protecting a vehicle from attack by a laser beam

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102015009353.3A DE102015009353A1 (en) 2015-07-17 2015-07-17 Method of protecting a vehicle from attack by a laser beam
EP16001535.0A EP3118563B1 (en) 2015-07-17 2016-07-12 Method for protecting a vehicle against an attack by a laser beam

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US20080190274A1 (en) * 2005-06-24 2008-08-14 Honeywell International Inc. Commercial airliner missile protection using formation drone aircraft
US20110030537A1 (en) * 2004-04-07 2011-02-10 Mullen Jeffrey D Advanced cooperative defensive military tactics, armor, and systems

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SE519866C2 (en) * 2000-08-17 2003-04-15 Celsiustech Electronics Ab Procedure to interfere and possibly damage a laser device and a protection
IT1391858B1 (en) * 2008-09-09 2012-01-27 Alenia Aeronautica Spa Test arrangement for a recognition of threats laser system for an aircraft
US9134174B2 (en) * 2013-01-07 2015-09-15 The Boeing Company Laser detection and warning system
US9970811B2 (en) * 2013-08-30 2018-05-15 Torrey Pines Logic, Inc. Passive, wide-spectral-band laser threat sensor

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Publication number Priority date Publication date Assignee Title
US7053812B2 (en) * 2003-12-18 2006-05-30 Textron Systems Corporation Recoverable pod for self-protection of aircraft and method of protecting an aircraft using a recoverable pod
US20110030537A1 (en) * 2004-04-07 2011-02-10 Mullen Jeffrey D Advanced cooperative defensive military tactics, armor, and systems
US20080190274A1 (en) * 2005-06-24 2008-08-14 Honeywell International Inc. Commercial airliner missile protection using formation drone aircraft

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EP3118563B1 (en) 2018-09-12
EP3118563A1 (en) 2017-01-18

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